Separable airplane for safe flying



Aug. 23, 1949. D. WEISZ SEPARABLE AIRPLANE FOR SAFE FLYING 2 Sheets-Sheet 1 Filed Nov. 7, 1946 INVENTOR. P/Wf 14 5/5 Aug. 23,1949. 7 D. WElSZ SEPARABLE AIRPLANE FOR SAFE FLYING v 2 Sheets-Sheet 2 Filed Nov. 7, 1946 arc INVENTOR.

bi ali'bme v.

Patented Aug. 23, 1949 UNITED STATES PATENT OFFICE 7 Claims. 1

This invention relates to air craft, particularly heavier than air flying machines, and has for its main object to provide an aircraft in which there will be separable parts temporarily connected when flying, and each part will be adapted to fly alone when any damage or accident happens to the other part, thereby greatly enhancing the safety of flying of such combination aircraft.

Particularly, my invention relates to airplanes,

and has for its main object to provide two airplanes, each with a single wing, which airplanes may be quickly and easily secured together into a double decker or two winged airplane, or may then be separated with the same ease and quickness, when either of single airplanes will be adapted to fly alone.

Another object of my invention is to provide an upper and a lower wing single decker airplane, which will be practically identical, having the same weight, and Well balanced, with the exception of hav ng oppositely placed wings andfuselages, and havin said fuselages secured, to one another with the mentioned quickly operable or disconnectable means. and also having quick and easy facilities, whereby all the crew, passengers and load from one fusela e may be transferred into the other one, and whereupon the emptied fuselage may be separated from the loaded one and abandoned, while the loaded one may carry all the Weight alone and safely fly on. In this manner, if either one of the component airplanes is damaged while flying, the undamaged one can continue in flight, and save all the passengers and load.

Still a further object of this invention is to provide a double decker combination airplane, composed of two single airplanes, wherein the fuselages are temporarily secured to one another in an air and water tight but quickly separable manner, wherein registering door openings are pro-.

'vided in the adjacent walls of the fuselages,

thereby allowing the passengers and load in one fuselage to be quickly transferred into the other one, but wherein doors are provided for such openings which may be quickly and easily closed. after the separation of the fuselages, and wherein such doors will have a tendency to automatically close by the action of the air stream caused by the flying of the separated single airplane.

Still a further object of my invention is to provide a double decker combination airplane, composed of two single decker airplanes, wherein the fusel-ages are secured to one another, and wherein, normally, the two fuselages are out of the center line, to make them balance, but wherein 2 means are provided that, upon separation, the fuselage of the separated single airplane will be quickly and easily moved in the center thereof, balancing when flying alone.

Still another object of my invention is to provide two single decker airplanes and means to comprise them into one double decker, said means being easily and quickly separable, and as easily and quickly releasable, whereby either part of the double decker airplane may keep on flying as a single airplane, and to provide means to extend the wing spread of either of the single airplanes when the same is to be flown alone, so as to enable it to carry the combined load of the two airplanes when two wings were carrying it.

Still further objects of this invent on will be partly apparent as the s ecification of the same proceeds, or will be partly pointed out therein,

and, among others. I may mention: to provide a safe separable aircraft. as indicated hereinbefore, wh c will be nest in appearance, simple in construction. and easy in use.

It will be seen that I provide a combination double decker airp ane, composed of two single wing airp anes. which will at ain all the objects of this invention, as indicated hereinbefore. It also be will be seen that. while preferably the crew will operate the devices for securing together and se aratin the two fuselages, the passengers or anybody e se may do the same in an emergency. very quickly and easily. In the embodiment shown, such a connection or disconnectlon may be executed simply by the throwing of one cam action lever.

My double decker combination airplane will insure greater safety to flying than is'the case at present, since, even if parachutes are provided in a flying machine used at present, many people are not able to skillfully use the parachute, particularly children, old and sick people, the descent by a parachute is always connected with various chances and accidents, and, finally, a great percentage of the damage, injury, and accidents occurring in flying machines, are such that no parachutes could be used, while in most of these cases, my invention will provide safety for the passengers and even for the load.

The damaged plane of my invention sometimes will simply be dropped, or it also may land easier because there is no load in it, and may be saved and repaired. A'pilot may volunteer to operate it.

In the drawings forming a part of this specification, and accompanying the same:

' Fig. 1 is a diagrammatical plan view of my separable double airplane, portions of the same being broken away, and

Fig. 2 is a side view thereof;

Fig. 3 is a front elevational view, partly in sec tion, of one of the two units which make up my separable combination double airplane, showing the unit with an overhead Wing, and

Fig. 4 is a similar front elevational view of the other unit in,my=double airplane, tthisibeing shown as having. alow i g;

Fig. 5 is a partly sectional diagrammatical front view of the two airplanes secured together, and forming my double separable airplane;

Fig. 6 is a fragmentary section-al-viewthrough the adjacent walls of the two airplaneiunitssseparably interconnected, and

Fig. 7 is a horizontal sectional iviewrtherethrough, the section being taken on .the line 'I-'! of Fig. 6;

Fig. 8 is a fragmentary elevational view of one of the-ad-j acent walls im-my two airplane units, {their securing means having been removed "for "clearnessof showing,-and

Fig. 9 is a fragmentary sectional 'view of said two walls; t-he section being'taken' about on the *Fig. '10 is--a-fragnrentary sectional view of the "mechanism -to;move the wings in "the'two' units -o'f "my -'airpla-ne '-:to central *ba'lance'd pos'iti0ns, -when the two -units are separated from one 'another, 'or when they are {to he-secured together;

Fig. *ll'is a plan view 'thereof, portions of the same having' beenremoved, and

Fi '12 is :a sectional "view showing the sliding interconnection-"between the fuselage 'of a unit airplane in my double combination -a-irplane,and themechanismtmmove the wing "withzrefer'ence to the fuselage' -thereon, the-section being-taken on the line ii-12" of Fig--11;

"Figfl3 indicates in a--diagrammatical manner anextension-mechanism ior the wing -of *my-airplane, and

Ir in-"l4 is a sectional viewthereofythe section being -taken on the line -l4--1"4 of Fig. 1 3;

Fig. 15 is a dist-grammatical view of =myd0uble decker airplane beforeseparating the two single --"-ones, because omenginestopped;

Fig: l6-shows the damagedsingle airplane separated and abandoned;

Fig. l l is -a View of the undamaged airplane "loaded' with passengers from both single iLlIIltS.

"Referring now to *the drawings --more' in detail, *by -characters (if reference-the numeral findicates my double separable :airplanedor safe'zfiyunit thereof "in tthe'ifonmrof a single airplane, "indicated generally :hy 'ithe murneral 112d, ;-1and=-.a

' right hand-.such-sunit D1. 'singlerainplanefld. :The

leit handzaum't: 2:1 iis'a'mdicatedsomewhat :mor detail, butstill diagrammatically/and in ad ,on ielevatiominvEig. ;3,-m:nd =,the;r13ig'hthand unitgzz is .-;similai1l shown tin Fig. 4,--.andit= wi11 h een that ithe leftihand- (unihhas: an -.unper win :23, .a 'riuselage 2A suspended-zthereirom, latfront under- -carniag -torllandingzgear:2 .and aarear landing ear..2fi. illwoieneines ,21; and ZiLarrfiL fl in th wing 23 are shown,; f or qdrivlngtsaid .,l eft hand sunitainplane.

*JI-fhe: [right hand -,unit .22 ..(.FZig.--.4) has .a lower wing 19, ,a ,fuselage g3!) isupported. 1thereon, -a .front -undercarriage.3il ,.a .reanundercarriage t or. .l,andin gear 32 :and also .has .twoenginesi and .35 in its wing 29 for motivepower. I

.Itiwillbe seen that .theiusjlage r gbody'zg of the left hand airplane is to the'left of the center 4 line 35 thereof, while the fuselage or body 30 of th right hand unit is at the right side of its center line 36.

Now, according to my invention, the two unit airplanes 2| and 22 will be secured together in an easily releasable but still safe and reliable manner, so that in such as position, the two units will form a single double winged or double decker ,airplanc, asindicat d iniEie. 5- Eonthiap rm thezinner wall 2.4a of thel'left hand fuselage 24 will be placed against the inner wall 30a of the fuselage 30 of the right hand unit airplane 22, and the two adjacent walls will be secured to one --:another iin-x such position, by easily operated, o iick but still strong, reliable means, said means having the character of being releasable in the .-,:same;easyrandnuick,manner.

It .Will be seen that I produce a double decker airplane having two fnselages side by side, and closely attached to one another, secured together -'-i-n 'a temporary ithough :reliableandqflckly releasable imanner. 'TIpreferablyiprovidadoonopen- :-'ings it! iii .-the wall-feta :of the :leittha-nd unit, :and similar Wegldteliing iflOOL vopenings 738 :in the wall 25 5600 of the might 'zhand-ifnselagexim. "These new operiings-normally, will 2bezkept-iunobstructed, .so

thatzthe occuparits:of;pne.:airplaneiunitimayieasily and: quickl sstep =vover: -tl'1ro1ightithe $1001. {openings Efrem yon-e: iintoi the other, when idesiredxand .ithe

basic :conception :of "my. inventinn is 1: that meremallmsand iin 'ithe :overwhelming :maioritymiithe epants :may-iquicklyz move into the adjacent. intact mania-whereupon theztwo units'imay be separated,

and the intact unit may keep-.011 fiy 'rl 'iwitheits :idQliblG 'fil ight, iandrsane :the ipeople.

'iE-ri, a;-.wo1id,- Sit is; as theloccupantsof any-separableidoubleeairplane 'woul'd'i'have a achoiee all 40 thextimefibetween rthe. two airplanes :in -whiehzto montinue the'itravelling,iandnsince the chances itha't both air-planes :will be Edamaged at thersame etime-tare iinfin'itely smallerithan ithezchances ithat onewof ithemwmay oe damaged, the safety of the 5 mucupants is many times :greater :than if =ttliey 'could rely up'ontonly one rsingleairplaneiin which they travel, as is fthe: case at present.

In Figsp6 and l l showone'for-m' for the quick aseouring'of the itwo airplane unitsvto' one an- -other, orreleasi-ng them i-nnasimilar manner.

iqs will be 'seenAin saidfigures, 'the numera' lflda indicates"the inner wall =of the =le'ft hand airplane unit, while the numerals 31 and 38 indicate the "respective -=co-eperating door openings, Fig. 6

showin g them with the oors *ISZHOVGG.

ll.e g-ister-ing-upper openings*8?) and l'll, and 'lower -openings-4 l -and'-'42,'are arranged in-the walls 2 2a and We. respectively, and a cam action hinged lever-#8 is pivoted Fin each ---opening 56, as at 4 3,

every qpeningffl. A 'cam action hook device #311 is at-the inner end 'of the pivoted lever 4'3, While the outer branch of the leven-is' pivotally connected-finto tan-operating rod %,as at M.

"As 'has'been"mentioned, ever-y registering pair ,of -qpenings 39and 40 will have suchapivoted leverarranged-therein;all the*levers'beingpivoted.

in the operating rod 46, and a handle 13 is secured atJan appropriate place onthe operating lQd Mkby'whichthe same "maybe -moved ill a right-hand direction, as indicated by-the arrow 4,3, 'nor ;a"left "hand direction, as shown by'ar- ,;.r0w$

'75 "It"WiIPbe-seen-that, whenthe handle #8 and 5 the operating rod 46 therewith, are moved in a right hand direction, arrow 49, all the cam action hooks 43a will tightly and securely engage the respective pins 45, and obviously said}, cam action will cause the adjacent walls 24a and 30a to be drawn close to one another.

To make the connection between the twoairplane bodies or fuselages more airtight and watertight, I may interpose a sealing material, indicated at 5!, between the two walls. as will be understood by those versed in this art.

For the lower openings 4| and 42, similar cam action hook levers 52 may be arranged, pivoted in a longitudinal rod 53, and provided with the operating handle 54. To secure the two fuselages in such connected position, I may also employ a locking pin 55 for each operating rod systems 46 and 53, respectively, said pin being dropped through an appropriate hole in a stationary part 56 on the respective fuselage wall, and then inserted into an aperture 51 in the pivot levers 43 and 52, respectively. When it is desiredto remove these locking means, and separate the two fuselages, pins 55 will be pulled out from the aperture in the stationary member 56 and the aperture 5'! in the respective pivot lever, and thereby permit the opening movement of all said levers.

In Figs. 8 and 9 I indicate one preferred form of doors employed in said openings 31, and 38, so that when the separation of the two airplane units has been completed, the one keeping on flying can be closed and sealed at the open side, by moving the doors into closure positions, and locking them in such a position. I preferably employ sliding doors 58 to close the respective door openings 31 and 38, or to release them by sliding into appropriate spaces 59 in the respec tive walls 24a and 30a. The same precautions may be resorted to with the plane to be abandoned.

In Figs. 8 and 9 some of the doors are shown in a closed, and others in an open, position. I also may provide T-shaped heads 50 for the sliding door, the under portion of the head of the T being arranged against the air stream, so that the doors will be automatically closed and kept closed when flying the unit, even if the other mechanical means for the said purpose are not used. For this effect the direction of the flying of the airplane is imagined as indicated by the arrow 5|.

When one of the units of my double airplane has been injured, and the intact unit is separated therefrom and is flown as a single decker airplane, the fuselage thereof must be moved to the right, in case of the left hand unit, or to the left, in the case of the right hand unit, so that the center line of the fuselage should now be at the centerline of the respective unit, for obvious balancing and flying reasons.

In Figs. 10 to 12 I show one form of construction, and means to accomplish this object. The arrangement here is shown for the left hand unit, but, of course, the identical construction will be employed for the right hand unit, only operating in a reverse direction.

In Figs. 10 to 12, the wing 23 is provided with a rack 62, which co-operates with a tooth segment 53, rotatably secured in the fuselage 24, and operable by the handle 64. It will be seen that if the handle 64 is moved in the right hand direction, arrow 55, wing 23 will be moved to the left, arrow 56, and the fuselage 24 may this way be placed on the center line of the wing. In Fig. 12 I show one form of sliding interconnection between the wing 23 and the fuselage 24, and it will be seen that according to this solution of the problem, the wing will have grooves 151, in which may slide the T rails 58 of the fuselage.

A releasable locking pin 63a may be used in cooperation with holes 63b to secure the toothed segment in either of its positions. It also will be obvious that when the load of a double decker airplane is moved into a single decker, the wing of the latter must have a larger spread, substantially the same as the spread of th two wings was before.

In Figs. 13 to 14, one solution of this problem is shown. According to this construction, a slidable extension 69 is arranged in the end of each wing, the drawing showing the right hand end of the wing 23. A coiled spring 10, normally withdraws the extension 69 into the wing 23, and keeps it in such a withdrawn position. When it is desired to extend the spread of the wing to a desired extent, cords ll, secured on the inner end of the wing extension 29, as at 12, will be pulled by the pilot inwardly, arrow 13, said cords passing through holes in the wing 23 and over pulleys 14. In this manner, obviously, the extension 59 i will be moved outwardly to a desired distance.

If the wing spread is to be shortened, the cords II will be released and permitted to ride in a direction opposite to that indicated by the arrow 13, which they will do after such release through the influence of the spring 10, and the extension 69 will be withdrawn to the extent permitted by the outward movement of the cords I l In Figs. 3, 4 and 5, the numerals 24b and 30b indicate windows for the'single airplanes. The circles in the showing of engines and propellers 21, 33 and 34 in Figs. 5, 15, 16 and 17 indicate that these engines and propellers are rotating in working order, while the full showing of the propeller at 28 indicates that that engine developed trouble, and this is the cause why the single airplane 2! is to be abandoned, and the airplane 22 will keep on flying.

I may mention that the undamaged plane may again be paired with an appropriate second plane, to replace the damaged one, and a new such double decker airplane produced with one half of the expense.

It also will be understood that the two single planes must be operated in harmony when they are connected into a double decker. This may be attained by various methods, well known to those versed in this art.

Also, when moving the fuselage in the airplane continuing the flight, the various electrical and other connections will be made in such a manner that they will not be changed by such comparatively small moving of the fuselage. In a word, such connections, like wiring, tubing, etc. will be made in a yielding and continuing manner, so that they will operate in any relative position between wing and fuselage within the limit of the movement of the wing against the fuselage. Such connection will be obvious to experts in airplane design.

It also may be noted that the elevator planes 21a and 22a of the single airplanes (Figs. 1 and 2) will be longer and narrower than usual in such planes. However, on account of their length, they will have the same surface as elevator planes as in a normal case. The reason for this alteration is obvious, and it is done to permit the securing together of the two fuselages without the elevator planes interfering, with one another.

It also will be obvious that the openings for the securing means 39, 40, 4| and 42 will have to be ,whenthe airplanes fly singly. Ialso want it 7 ention that in case of war; the occupantsio'f th'e double safety airplane 9f my invention, will, in most cases, be able tolgeepon flyingeven if ,ongegn lr of the double airplane Will be" damaged, and so'avo idbeing'taken prisoners'of war.

"The cost'of manufacturing of my double air pnoe will not be 'very materially more than a single one, but the advantages accompanying; its isejwill greatly outweigh the increasing cost, and ultimately, in case of accident, the cost will really be less, than that of a Single aircraft, since part orul machine can again be used. For thesame reason, even if the passengers in such a'double combination airplane may have to pay higher re, thesafety and the avoidance of accidents will make the higherfare really much lowerth'an thosefoharged at present, In a Way Imay say that with one single step, a passenger in my dou ble airplanemay avoid possibly fatal accidents, stepinto another airplane which is still able t fly. f i It also may be of advantage to provide guards at appropriate places for the propellersfand engines of mysingle airplanes, such guards preferably being provided below the propellers of the upper wing and above the propellers of the lower wing, whereby the possibility of injury tothe pro; pel er of the undamaged airplane by'parts, or the propeller of the damaged one, will be avoided.

'Vlfhen my airplane flies as a single one [with extended wing spread, after some such flight, the usedup fuel will gradually reduce the weight, and the wing spread may again be reduced. A t the same time, the speed may be increased.

It also will be obvious that the actual practical bu'lding of double decker safety airplanes comed of two single decker planes, according to invention, will have many details not shown i my, drawings, as further experimenting and actual trials will lead to most efficient solutions of the various detail problems, and so, whileI have shown a preferred embodiment of my invention, it is to be understood that changes and variations may be resorted to in the elements, combinations and co-operations in my invention, and I reserve my rights to such changes and variations, as are within the spirit of this speciligation, and the scope of the claims hereunto s o enoed. I

i What I claim as new, and want to protect by Letters Patent of the United States, is:

1. A composite biplane comprising two monoplanes, one monoplane having a high wing and a fuselage depending therefrom on the one side of its center, and the other monoplane having a low wing with a fuselage built thereon somewhat out ofthe center in the other direction, the two fuselages being constructed and arranged to be placed into a side by side relation, and means to quickly and easily secure the two fuselages to one another or to separate them. l 2. In a composite biplane, as set forth in claim 1, registering openings in the adjacent walls of the .fuselages, normally being open to permit a quick transfer of the passengers and load from one fuselage into the other, and doors in said openings adapted to be sealed and locked when the mon0planes are operated.

3. In a composite biplane, as set forth in claim 1, registering openings in the adjacent walls'of the fuselages, normally being open to permit a quick transfer of the passengers and load from one fuselage into the other, and doors in .said epenines adapted to be sealed and loclged when t d, sa d dents bein f e Js rs l d atfthefend thereof "of flight, whereby the lene er bi flying, w dl dbqr' into a closed air stream, w automatically position.

,4, Ina comPQsite biplan as. set forth in claim 1, 1 niean'sitd'slee re to giethfiriorSeparate the two fuselages ln eluding a pair of registering openings in the'adja centwallsof the two fuselages, a. leverfwith a cam hgoktermination, pivcited on a member securedi'n one opening, a second memberslebl redin the other opening, said termination'being adaptedto :engageor disen age said second member, id' leverhaving a branch pr jecting froin'said'pivot intothe fuselage of said first'opening,"whereby' a moving of said projecting branch mo s direction will hook said 20 leverv into said .fir st...member, and secure the two fuselages'to'gether, and a'moving thereof in the other directionwill release said member and release'the'two'fuslagesf'from one another.

5. Ina .cpmp'q'sitebiplane; as set forth in claim 1, said means'to secure together or separate the two fuselagescomp' inga plurality of registering pairs of holes adjacent walls of the two fuselages, a lever'withfafcam hook termination pivoted on a me o; securedin'one opening in each pair, a seconglniernber secured in the other opening," said hdokftermination' being adapted to engage or disengage said, second member, said lever having a branch .prgjjecting from said pivot into the fuselage or saidfirst opening, "whereby a moving of saidprojiectin'gj branch in one direction will hook .said lever unto said second member and secure thetwoiuselagestogether, and a moving thereof irrthe" ther'fdirection will release saidseeond member andfrelease the two fuselages from o'rieanother, an operating rod in said first fuselage th r9 ,ctir s 1e b a c e be n pivl ,1,8, asset forth in claim eifthe f respective ifuselages" in the 6, ,esterrqsiuons. When the sin le idj'means to move the q pperating sliding eled thewins'. spectively. t ,d toothed segment for a nd a handle on the efsa in e Or the agtvnv warez.

$ 91 9n i 1are o re r i th fi this s 

